Dynamic composite distortion simulator and its working method

Abstract

The present invention discloses a dynamic composite distortion simulator and a working method thereof in the technical field of aero-engine air inlet and engine matching. The simulator comprises a process air inlet, a spoiler column, a rotary valve and a high-speed motor. The spoiler column is installed inside the process air inlet, and the rotary valve is installed in the cavity of the spoiler column. One end of the rotary valve extending out of the spoiler column is connected to the high-speed motor. Dynamic distortion vortices are formed by utilizing the flow around the column and the rotary valve, and parameters such as the intensity and scale frequency of the vortex change with changes in the motor speed and the angle of attack and height of the spoiler column. This can effectively simulate the dynamic distortion flow field structure generated in the air inlet due to various reasons, overcome the shortcomings of existing simulators in simulating dynamic distortion, form a flow structure similar to the distortion flow field at the outlet of the real air inlet, so as to more realistically simulate the air inlet matching process, significantly improve the experimental efficiency and accuracy, and do not require an external air source.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine air inlet and engine matching, and in particular to a dynamic composite distortion simulator and a working method thereof. Background Art

[0002] Modern advanced military aircraft require high maneuverability and high stealth performance. To meet these constraints, they commonly utilize large-curvature S-bend inlets. Due to inlet lip separation and strong internal adverse pressure gradients, the flow inside these S-bend inlets deteriorates, forming large-scale separated vortices and causing outlet distortion. Inlet outlet distortion can affect the stable operation of the downstream fan and, in severe cases, can cause stall and surge. Therefore, to ensure stable and efficient engine operation, thorough inlet-engine matching testing is essential.

[0003] Currently, inlet-to-exit matching tests typically use structures such as distortion plates and meshes to simulate the distortion profile of the inlet exit cross-section. This is then connected to the downstream engine for inlet-to-exit matching tests. This distortion simulation method simplifies the three-dimensional, unsteady, distorted flow field at the inlet exit into a two-dimensional, steady distortion profile. This differs from the actual distorted flow field, and the resulting inlet-to-exit matching performance also deviates from the true value. Summary of the Invention

[0004] This invention provides a dynamic composite distortion simulator and its operating method. This device addresses the shortcomings of existing technologies and simulates the three-dimensional unsteady distorted flow field structure at the inlet exit, ensuring that the inlet-exit matching test is closer to the actual value. The device can realistically simulate the dynamic distorted vortex structure at the inlet exit, allowing for more accurate testing of inlet-exit matching performance.

[0005] The present invention provides a dynamic composite distortion simulator and a working method thereof, which adopts the following technical solution: comprising a process air inlet, a spoiler column, a rotary valve and a high-speed motor, wherein the spoiler column is installed inside the process air inlet, the rotary valve is installed in the cavity of the spoiler column, and one end of the rotary valve extends out of the spoiler column and is connected to the high-speed motor.

[0006] By adopting the above technical solution, a high-speed motor drives the rotary valve to rotate, and the incoming flow forms a distorted vortex group downstream after passing through the spoiler column. As the internal channel of the flow column opens and closes, the low-energy flow behind the flow column is periodically blown away, causing dynamic changes in the downstream distorted vortex group, thereby forming a dynamic compound distortion.

[0007] Optionally, the ratio of the height H of the spoiler column in the radial direction to the inner diameter d of the process air inlet duct is 0.1-0.65, the ratio of the length l1 of the spoiler column to the inner diameter d of the process air inlet duct is 0.3-0.8, the leading edge chamfer radius R1 of the spoiler column is 2-10mm, the trailing edge chamfer radius R2 of the spoiler column is 2-10mm, the ratio of the distance d1 of the inner channel central axis position of the spoiler column from the leading edge of the spoiler column to the length l1 of the spoiler column is 0.3-0.8, the ratio of the channel inlet and outlet width d2 of the spoiler column to the length l1 of the spoiler column is 0.2-0.8, the ratio of the channel height h of the spoiler column to the height H of the spoiler column is 0.5-0.8, the central angle θ of the arc cavity in the channel of the spoiler column ranges from 30-120 degrees, and the radius R3 is 0.5-0.8 times the channel width d2.

[0008] Optionally, the angle α between the windward surface A and the windward surface B of the spoiler column is 15-60 degrees, the angle β between the windward surface A and the leeward surface C of the spoiler column is 15-60 degrees, and the angle γ between the windward surface A of the spoiler column and the central axis direction of the process air inlet is 0-45 degrees.

[0009] Optionally, the process air inlet is a cylinder, the inner diameter d of the process air inlet is consistent with the inner diameter of the engine inlet to be matched downstream, the length L of the process air inlet is selected according to the inner diameter d, L / d is 3-6, and the ratio of the length L1 of the leading edge of the spoiler column installation position from the process air inlet inlet to the inner diameter d of the process air inlet is 1-3.

[0010] Optionally, the rotation radius R4 of the rotary valve is 1-2 mm smaller than the arc-shaped cavity R3 of the spoiler column, the ratio of the baffle height h1 of the rotary valve to the channel height h of the spoiler column is 0.8-1, and the baffle thickness δ is 1-15 mm.

[0011] Optionally, the high-speed motor is required to be able to drive the rotary valve to overcome wind resistance and rotate at a constant speed, and the adjustable speed range is 0-20000r / min.

[0012] Optionally, the method further includes a working method of the dynamic composite distortion simulator, specifically comprising the following steps:

[0013] S1: The incoming flow passes through the spoiler column to form a vortex of swirl and total pressure composite distortion;

[0014] S2: As the rotary valve 3 rotates, the spoiler column 2 will periodically enter the full flow state, the intermediate state, and the no flow state. Therefore, the low-energy flow behind the spoiler column 2 is periodically blown away. The airflow distortion value at the outlet of the process inlet duct 1 reaches the maximum in the no flow state and gradually decreases. It reaches the minimum distortion value in the full flow state to complete a cycle, thus causing dynamic compound distortion.

[0015] S3: By changing the speed of the high-speed motor and the angle of attack and height parameters of the spoiler, the frequency, size, and intensity parameters of the downstream distortion vortex are adjusted to make them close to the dynamic distortion flow field characteristics of the actual inlet outlet, thereby more realistically simulating the inlet outlet distortion.

[0016] In summary, the present invention has at least one of the following beneficial effects:

[0017] 1. By using the flow column and rotating valve, a dynamic swirl and total pressure composite distortion vortex is formed. The vortex parameters such as intensity and scale frequency change with the changes in motor speed and the angle of attack and height of the spoiler column. This can effectively simulate the dynamic distortion flow field structure caused by various reasons in the inlet duct, overcome the shortcomings of existing simulators in simulating dynamic distortion, and form a flow structure similar to the actual inlet duct outlet distortion flow field, so as to more realistically simulate the inlet matching process.

[0018] 2. Simple structure, easy operation, significantly improving experimental efficiency and accuracy.

[0019] 3. No external gas source is required, and dynamic distortion is generated by passive jet. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0021] Figure 1 It is a schematic diagram of the structure of the present invention;

[0022] Figure 2 This is a schematic diagram of the air inlet of the process of the present invention;

[0023] Figure 3 Schematic diagram of the spoiler column of the present invention;

[0024] Figure 4 This is a schematic diagram of a rotary valve of the present invention;

[0025] Figure 5 It is a schematic diagram of the working principle of the present invention.

[0026] Explanation of the accompanying symbols: 1. process air inlet; 2. spoiler column; 3. rotary valve; 4. high-speed motor. DETAILED DESCRIPTION

[0027] The following is combined with Figure 1-5 The present invention is described in further detail. Example

[0028] Reference Figure 1 The present invention discloses a dynamic composite distortion simulator, whose structure includes a process air inlet 1, a spoiler column 2, a rotary valve 3 and a high-speed motor 4, wherein the spoiler column 2 is installed inside the process air inlet 1, and the rotary valve 3 is installed in the cavity of the spoiler column 2 and is connected to the high-speed motor 4. The high-speed motor 4 drives the rotary valve 3 to rotate, and the incoming flow forms a distorted vortex group downstream after passing through the spoiler column, and as the internal channel of the spoiler column is opened and closed, the low-energy flow behind the spoiler column is periodically blown away, causing dynamic changes in the downstream distorted vortex group, thereby forming a dynamic composite distortion.

[0029] Reference Figure 2 The process air inlet 1 is a cylinder, and the inner diameter d of the process air inlet 1 is consistent with the inner diameter of the engine inlet to be matched downstream. The length L of the process air inlet 1 is selected according to the inner diameter d, L / d is 3, and the ratio of the length L1 from the leading edge of the installation position of the spoiler column 2 to the inlet of the process air inlet 1 to the inner diameter d of the process air inlet 1 is 1.

[0030] Reference Figure 3 , the ratio of the height H of the spoiler column 2 in the radial direction to the inner diameter d of the process air inlet 1 is 0.5, the ratio of the length l1 of the spoiler column 2 to the inner diameter d of the process air inlet 1 is 0.8, the leading edge chamfer radius R1 of the spoiler column 2 is 10mm, the trailing edge chamfer radius R2 of the spoiler column 2 is 10mm, the ratio of the distance d1 of the central axis position of the inner channel of the spoiler column 2 from the leading edge of the spoiler column 2 to the length l1 of the spoiler column 2 is 0.6, the ratio of the channel inlet and outlet width d2 of the spoiler column 2 to the length l1 of the spoiler column 2 is 0.5, the ratio of the channel height h of the spoiler column 2 to the height H of the spoiler column 2 is 0.7, the central angle θ of the arc cavity in the channel of the spoiler column 2 ranges from 60 degrees, and the radius R3 is 0.55 times the channel width d2.

[0031] The angle α between the windward surface A and the windward surface B of the spoiler column 2 is 45 degrees, the angle β between the windward surface A and the leeward surface C of the spoiler column 2 is 45 degrees, and the angle γ between the windward surface A of the spoiler column 2 and the central axis direction of the process air inlet 1 is 30 degrees.

[0032] Reference Figure 4 The rotation radius R4 of the rotary valve 3 is 1 mm smaller than the arc-shaped cavity R3 of the spoiler column 2, the ratio of the baffle height h1 of the rotary valve 3 to the channel height h of the spoiler column 2 is 1, and the baffle thickness δ is 3 mm. Example

[0033] The working method of dynamic composite distortion simulator is as follows: Figure 5 , including a full flow state, an intermediate state and a no flow state, specifically including the following steps:

[0034] S1: The incoming flow passes through the spoiler column 2 to form a vortex of swirl and total pressure composite distortion;

[0035] S2: As the rotary valve 3 rotates, the spoiler column 2 will periodically enter the full flow state, the intermediate state, and the no flow state. Therefore, the low-energy flow behind the spoiler column 2 is periodically blown away. The airflow distortion value at the outlet of the process inlet duct 1 reaches the maximum in the no flow state and gradually decreases. It reaches the minimum distortion value in the full flow state to complete a cycle, thus causing dynamic compound distortion.

[0036] S3: By changing the speed of the high-speed motor 4 and the parameters such as the angle of attack and height of the spoiler 2, the frequency, size, intensity and other parameters of the downstream distortion vortex are adjusted to make them close to the dynamic distortion flow field characteristics of the actual inlet outlet, so as to more realistically simulate the inlet outlet distortion.

[0037] The above are all preferred embodiments of the present invention, and are not intended to limit the scope of protection of the present invention. Therefore, any equivalent changes made based on the structure, shape, and principle of the present invention should be included in the scope of protection of the present invention.

Claims

1. Dynamic composite distortion simulator, characterized by: It includes a process air inlet (1), a spoiler column (2), a rotary valve (3) and a high-speed motor (4). The spoiler column (2) is installed inside the process air inlet (1), the rotary valve (3) is installed in the cavity of the spoiler column (2), and one end of the rotary valve (3) extending out of the spoiler column (2) is connected to the high-speed motor (4); The included angle α between the windward surface A and the windward surface B of the spoiler column (2) is 15-60 degrees, the included angle β between the windward surface A and the leeward surface C of the spoiler column (2) is 15-60 degrees, and the included angle γ between the windward surface A of the spoiler column (2) and the central axis direction of the process air inlet duct (1) is 0-45 degrees; The rotation radius R4 of the rotary valve (3) is 1-2 mm smaller than the arc-shaped cavity R3 of the spoiler column (2), the ratio of the baffle height h1 of the rotary valve (3) to the channel height h of the spoiler column (2) is 0.8-1, and the baffle thickness δ is 1-15 mm.

2. The dynamic composite distortion simulator according to claim 1, characterized in that: The ratio of the height H of the spoiler column (2) in the radial direction to the inner diameter d of the process air inlet duct (1) is 0.1-0.65, the ratio of the length l1 of the spoiler column (2) to the inner diameter d of the process air inlet duct (1) is 0.3-0.8, the leading edge chamfer radius R1 of the spoiler column (2) is 2-10 mm, the trailing edge chamfer radius R2 of the spoiler column (2) is 2-10 mm, the position of the central axis of the inner channel of the spoiler column (2) is 0.1-0.65, the distance from the center of the spoiler column (2) to the inner diameter of the process air inlet duct (1) is 0.3-0.8, the leading edge chamfer radius R1 of the spoiler column (2) is 2-10 mm, the trailing edge chamfer radius R2 of the spoiler column (2) is 2-10 mm, and the distance from the center of the inner channel of the spoiler column (2) to the inner diameter of the process air inlet duct (1) is 0.1-0.

65. The ratio of the distance d1 of the leading edge to the length l1 of the spoiler column (2) is 0.3-0.8, the ratio of the inlet and outlet width d2 of the channel of the spoiler column (2) to the length l1 of the spoiler column (2) is 0.2-0.8, the ratio of the channel height h of the spoiler column (2) to the height H of the spoiler column (2) is 0.5-0.8, the central angle θ of the arc cavity in the channel of the spoiler column (2) ranges from 30 to 120 degrees, and the radius R3 is 0.5-0.8 times the channel width d2.

3. The dynamic composite distortion simulator according to claim 1, wherein: The process air inlet (1) is a cylinder, and the inner diameter d of the process air inlet (1) is consistent with the inner diameter of the engine inlet to be matched downstream. The length L of the process air inlet (1) is selected according to the inner diameter d, and L / d is 3-6. The ratio of the length L1 of the leading edge of the installation position of the spoiler column (2) from the inlet of the process air inlet (1) to the inner diameter d of the process air inlet (1) is 1-3.

4. The dynamic composite distortion simulator according to claim 1, characterized in that: The high-speed motor (4) rotates at a constant speed, and the adjustable speed range is 0-20000r / min.

5. The dynamic composite distortion simulator according to any one of claims 1 to 4, characterized in that: The invention also includes a working method of the dynamic composite distortion simulator, which specifically includes the following steps: S1: The incoming flow passes through the spoiler column (2) to form a vortex of swirl and total pressure composite distortion; S2: As the rotary valve (3) rotates, the spoiler column (2) periodically enters a full flow state, an intermediate state, and a no flow state, so the low-energy flow behind the spoiler column (2) is periodically blown away, and the airflow distortion value at the outlet of the process inlet duct (1) reaches a maximum in the no flow state and gradually decreases, reaching a minimum distortion value in the full flow state to complete a cycle, thereby causing dynamic compound distortion; S3: By changing the rotation speed of the high-speed motor (4) and the angle of attack and height parameters of the spoiler column (2), the frequency, size and intensity parameters of the downstream distortion vortex are adjusted to make them close to the dynamic distortion flow field characteristics of the real inlet outlet, so as to more realistically simulate the inlet outlet distortion.

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